CN113719358A - Heavy gas turbine control method, device, equipment and storage medium - Google Patents
Heavy gas turbine control method, device, equipment and storage medium Download PDFInfo
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- CN113719358A CN113719358A CN202111037159.7A CN202111037159A CN113719358A CN 113719358 A CN113719358 A CN 113719358A CN 202111037159 A CN202111037159 A CN 202111037159A CN 113719358 A CN113719358 A CN 113719358A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
Abstract
The invention discloses a heavy-duty gas turbine control method, a heavy-duty gas turbine control device, heavy-duty gas turbine control equipment and a storage medium. The method comprises the following steps: acquiring actual operation data of the gas turbine, and acquiring a turbine inlet temperature analytic value and a corresponding turbine inlet temperature confidence coefficient through a pre-trained turbine inlet parameter analytic model; determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the gas turbine; and when the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is smaller than the threshold of the confidence coefficient of the exhaust temperature, taking the minimum value of the fuel output quantity corresponding to the analytic value of the turbine inlet temperature and the fuel output quantity corresponding to the calculated value of the turbine exhaust temperature as a target fuel output quantity, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity. The invention can realize stable output of maximum power while avoiding the overtemperature damage of the gas turbine.
Description
Technical Field
The embodiment of the invention relates to the technical field of automatic control, in particular to a heavy-duty gas turbine control method, device, equipment and storage medium.
Background
The temperature control loop of the heavy-duty gas turbine avoids overtemperature damage of the gas turbine while ensuring that the gas turbine can reach the highest design point temperature to maximize the output.
At present, after an exhaust temperature measurement value and an exhaust temperature reference value are compared, the fuel quantity of a gas turbine is adjusted through a PI controller, and overtemperature alarm and overtemperature interruption are realized through comparing the exhaust temperature measurement value and the exhaust temperature reference value in the temperature protection of the gas turbine. The fault-tolerant control of the method is always positioned on one side of the exhaust temperature reference, namely a plurality of exhaust temperature reference lines are arranged so as to improve the fault-tolerant capability of the gas turbine. However, the fault tolerance of the measured value of the exhaust temperature is not considered in the method, when the exhaust temperature sensor fails, the average exhaust temperature is calculated by the average exhaust temperature algorithm after only eliminating the highest value, the lowest value and the bad value, so that the error of the average exhaust temperature calculation is large, and when the calculated value of the average exhaust temperature is small due to the failure of the temperature sensor, the actual inlet temperature of the controlled gas turbine is increased greatly, the overtemperature of the gas turbine is caused, the operation of overtemperature protection is not even caused, and the hot parts of the gas turbine are burnt out; when the average exhaust temperature calculated value is larger due to the fault of the temperature sensor, the actual inlet temperature of the controlled gas turbine is smaller, so that the maximum output power of the combustion engine cannot be reached.
Disclosure of Invention
The invention provides a heavy-duty gas turbine control method, a heavy-duty gas turbine control device, heavy-duty gas turbine control equipment and a storage medium, which are used for avoiding the overtemperature damage of a gas turbine and realizing the stable output of maximum power.
In a first aspect, an embodiment of the present invention provides a heavy duty gas turbine control method, including:
acquiring actual operation data of the gas turbine, and obtaining a turbine inlet temperature analytic value and a corresponding turbine inlet temperature confidence coefficient through a pre-trained turbine inlet parameter analytic model, wherein the turbine inlet parameter analytic model comprises a turbine inlet temperature analytic model and a compressor outlet pressure analytic model;
determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the gas turbine;
and when the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is smaller than the threshold of the confidence coefficient of the exhaust temperature, taking the minimum value of the fuel output quantity corresponding to the analytic value of the turbine inlet temperature and the fuel output quantity corresponding to the calculated value of the turbine exhaust temperature as a target fuel output quantity, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
Optionally, obtaining a turbine inlet temperature analytic value and a corresponding turbine inlet temperature confidence through a turbine inlet parameter analytic model trained in advance includes:
respectively inputting the actual operation data of the gas turbine as input data into a turbine inlet temperature analytical model and a compressor outlet pressure analytical model which are trained in advance to obtain a turbine inlet temperature analytical value and a compressor outlet pressure analytical value;
and obtaining the analysis precision of the pressure at the outlet of the gas compressor according to the analysis value of the pressure at the outlet of the gas compressor, and taking the analysis precision of the pressure at the outlet of the gas compressor as the confidence coefficient of the temperature at the inlet of the turbine.
Optionally, the training process of the turbine inlet temperature analytic model includes:
acquiring historical gas turbine operation data and a corresponding turbine inlet temperature calculation value in a historical time period;
inputting the historical gas turbine operation data into a temperature analysis model to be trained to obtain an output turbine inlet temperature training value;
obtaining a temperature activation function according to the turbine inlet temperature training value and the turbine inlet temperature calculation value;
carrying out back propagation on the temperature analytic model to be trained through the temperature activation function to obtain the turbine inlet temperature analytic model;
the training process of the gas compressor outlet pressure analytic model comprises the following steps:
acquiring historical gas turbine operation data in a historical time period and corresponding gas compressor outlet pressure calculated values;
inputting the historical gas turbine operation data into a pressure analysis model to be trained to obtain an output compressor outlet pressure training value;
obtaining a pressure activation function according to the compressor outlet pressure training value and the compressor outlet pressure calculation value;
and performing back propagation on the pressure analytic model to be trained through the pressure activation function to obtain the compressor outlet pressure analytic model.
Optionally, the method further includes:
and when the turbine inlet temperature confidence coefficient is smaller than the inlet temperature confidence coefficient threshold or the turbine exhaust temperature confidence coefficient is larger than or equal to the exhaust temperature confidence coefficient threshold, taking the fuel output quantity corresponding to the turbine exhaust temperature calculation value as a target fuel output quantity, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
Optionally, the method further includes:
if the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature, when the analytic value of the turbine inlet temperature is greater than or equal to the threshold of the overtemperature of the inlet temperature or the calculated value of the turbine exhaust temperature is greater than or equal to the threshold of the overtemperature of the exhaust temperature, the overtemperature alarm operation of the gas turbine is carried out;
and if the confidence coefficient of the turbine inlet temperature is smaller than the threshold value of the confidence coefficient of the inlet temperature, when the calculated value of the turbine exhaust temperature is larger than or equal to the threshold value of the overtemperature of the exhaust temperature, performing overtemperature alarm operation on the gas turbine.
Optionally, the method further includes:
if the confidence coefficient of the turbine inlet temperature is smaller than the threshold of the confidence coefficient of the inlet temperature or the confidence coefficient of the turbine exhaust temperature is larger than or equal to the threshold of the confidence coefficient of the exhaust temperature, when the calculated value of the turbine exhaust temperature is larger than or equal to the threshold of the cutoff temperature of the exhaust temperature, the overtemperature cutoff operation of the gas turbine is carried out;
and if the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is smaller than the threshold of the confidence coefficient of the exhaust temperature, when the analytic value of the turbine inlet temperature is greater than or equal to the threshold of the inlet temperature interruption and the calculated value of the turbine exhaust temperature is greater than or equal to the threshold of the exhaust temperature interruption, performing the overtemperature interruption operation of the gas turbine.
Optionally, the actual operation data of the combustion engine includes: ambient temperature, ambient pressure, compressor inlet guide vane angle, compressor outlet pressure, turbine outlet pressure, combustion engine speed, fuel quantity, and/or turbine exhaust temperature.
In a second aspect, embodiments of the present invention further provide a heavy duty gas turbine control apparatus, the apparatus comprising:
the turbine inlet parameter analysis module is used for acquiring actual operation data of the gas turbine and obtaining a turbine inlet temperature analysis value and a corresponding turbine inlet temperature confidence coefficient through a pre-trained turbine inlet parameter analysis model, wherein the turbine inlet parameter analysis model comprises a turbine inlet temperature analysis model and a compressor outlet pressure analysis model;
the turbine exhaust parameter calculation module is used for determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the gas turbine;
and the first fuel control module is used for taking the minimum value of the fuel output quantity corresponding to the turbine inlet temperature analytic value and the fuel output quantity corresponding to the turbine exhaust temperature calculated value as a target fuel output quantity when the turbine inlet temperature confidence coefficient is greater than or equal to an inlet temperature confidence coefficient threshold and the turbine exhaust temperature confidence coefficient is smaller than an exhaust temperature confidence coefficient threshold, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
In a third aspect, embodiments of the present invention also provide heavy duty gas turbine control apparatus comprising:
one or more processors;
a memory for storing one or more programs;
the system comprises at least two signal collectors, a data acquisition unit and a data processing unit, wherein the signal collectors are used for collecting actual operation data of the combustion engine;
when executed by the one or more processors, cause the one or more processors to implement a heavy duty gas turbine control method according to any embodiment of the invention.
In a fourth aspect, embodiments of the present invention also provide a storage medium containing computer-executable instructions for performing a method of controlling a heavy duty gas turbine according to any of the embodiments of the present invention when executed by a computer processor.
The invention obtains the actual operation data of the gas turbine, obtains the turbine inlet temperature analytic value and the corresponding turbine inlet temperature confidence coefficient through the turbine inlet parameter analytic model trained in advance, wherein the turbine inlet parameter analysis model comprises a turbine inlet temperature analysis model and a compressor outlet pressure analysis model, determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the combustion engine, when the turbine inlet temperature confidence is greater than or equal to the inlet temperature confidence threshold and the turbine exhaust temperature confidence is less than the exhaust temperature confidence threshold, the minimum value of the fuel output quantity corresponding to the turbine inlet temperature analytic value and the fuel output quantity corresponding to the turbine exhaust temperature calculation value is used as the target fuel output quantity, and the operation of the heavy gas turbine is controlled according to the target fuel output quantity, and the invention can realize the stable output of maximum power while avoiding the overtemperature damage of the gas turbine.
Drawings
FIG. 1 is a flow chart of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention;
FIG. 2a is a schematic diagram illustrating a first principle in a method for controlling a heavy duty gas turbine according to a first embodiment of the present invention;
FIG. 2b is a schematic diagram illustrating a second principle of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention;
FIG. 2c is a schematic diagram illustrating a third principle of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention;
FIG. 2d is a fourth schematic diagram of a method for controlling a heavy duty gas turbine according to one embodiment of the present invention;
FIG. 2e is a schematic diagram illustrating a fifth principle of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention;
FIG. 2f is a sixth schematic illustration of a method of controlling a heavy duty gas turbine according to a first embodiment of the present invention;
FIG. 2g is a schematic diagram of a seventh principle in a method for controlling a heavy duty gas turbine according to an embodiment of the present invention
FIG. 3 is a block diagram of a heavy duty gas turbine control apparatus according to a second embodiment of the present invention;
fig. 4 is a block diagram of a heavy duty gas turbine control apparatus according to a third embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be noted that, for convenience of description, only a part of the structures related to the present invention, not all of the structures, are shown in the drawings, and furthermore, embodiments of the present invention and features of the embodiments may be combined with each other without conflict.
Example one
Fig. 1 is a flowchart of a heavy duty gas turbine control method according to an embodiment of the present invention, where the embodiment is applicable to a case where a temperature of a heavy duty gas turbine is controlled, and the method may be performed by a heavy duty gas turbine control apparatus, and the apparatus may be implemented by software and/or hardware.
As shown in fig. 1, the method specifically includes the following steps:
and step 110, acquiring actual operation data of the gas turbine, and obtaining a turbine inlet temperature analytic value and a corresponding turbine inlet temperature confidence coefficient through a pre-trained turbine inlet parameter analytic model.
The turbine inlet parameter analysis model can comprise a turbine inlet temperature analysis model and a compressor outlet pressure analysis model. The actual operating data of the combustion engine may include: ambient temperature, ambient pressure, compressor inlet guide vane angle, compressor outlet pressure, turbine outlet pressure, combustion engine speed, fuel quantity, and/or turbine exhaust temperature.
In this embodiment, obtaining a turbine inlet temperature analytic value and a corresponding turbine inlet temperature confidence by using a pre-trained turbine inlet parameter analytic model may be implemented by the following method: the method comprises the steps that actual operation data of the gas turbine are used as input data, and a turbine inlet temperature analytical model and a compressor outlet pressure analytical model which are trained in advance are respectively input to obtain a turbine inlet temperature analytical value and a compressor outlet pressure analytical value; and obtaining the analysis precision of the pressure at the outlet of the gas compressor according to the analysis value of the pressure at the outlet of the gas compressor, and taking the analysis precision of the pressure at the outlet of the gas compressor as the confidence coefficient of the temperature at the inlet of the turbine.
In practical applications, the training process of the turbine inlet temperature analytic model may include the following steps:
and S11, acquiring historical combustion engine operation data in historical time periods and corresponding turbine inlet temperature calculated values.
The historical gas turbine operation data at any moment can include the corresponding ambient temperature, ambient pressure, inlet guide vane angle of the gas compressor, outlet pressure of the turbine, rotating speed of the gas turbine, fuel quantity and/or exhaust temperature of the turbine at the moment.
Specifically, taking historical operating data of the combustion engine at a certain time as an example, the calculated value of the turbine inlet temperature corresponding to the time can be calculated through relevant parameters in the historical operating data of the combustion engine:
wherein, T3Can represent a calculated value of turbine inlet temperature, T4Can represent the turbine exhaust temperature, piTCan represent the turbo expansion ratio, kgCan express the gas adiabatic exponent, etaTTurbine efficiency can be expressed.
And S12, inputting historical combustion engine operation data into the temperature analysis model to be trained, and obtaining an output turbine inlet temperature training value.
Specifically, a nonlinear autoregressive neural network can be used to establish a temperature analytic model to be trained, and the model is defined as follows:
y(t)＝f(y(t-1),y(t-2),...,y(t-n),u(t-1),u(t-2),...,u(t-m))，
wherein y (t) can represent a training value of the turbine inlet temperature at the t moment, y (t-n) can represent a training value of the turbine inlet temperature at the t-n moment, u (t-m) can represent input parameters at the t-m moment, and the input parameters can comprise ambient temperature, ambient pressure, an angle of an inlet guide vane of a compressor, the rotating speed of a combustion engine, fuel quantity and the like. The function f can represent the functional relation between the input parameters and the turbine inlet temperature training values, the functional relation can be represented by a nonlinear autoregressive neural network, the neural network can be composed of 1 hidden layer and 1 output layer, and the neural network structure modification of the analytic model can be realized by increasing the number of layers of the hidden layer and the output layer. The network structure of the analytical model can be determined specifically according to the accuracy of the model training process.
And S13, obtaining a temperature activation function according to the turbine inlet temperature training value and the calculated value of the turbine inlet temperature.
And S14, reversely propagating the temperature analytic model to be trained through the temperature activation function to obtain the turbine inlet temperature analytic model.
Specifically, a non-linear autoregressive neural network is trained by using historical gas turbine operation data to obtain a temperature activation function, a temperature analysis model to be trained is subjected to back propagation, model parameters are continuously optimized, and a turbine inlet temperature analysis model is obtained.
The training process of the gas compressor outlet pressure analytic model comprises the following steps:
and S21, acquiring historical combustion engine operation data in historical time periods and corresponding calculated values of the compressor outlet pressure.
And S22, inputting historical gas turbine operation data into the pressure analysis model to be trained, and obtaining an output compressor outlet pressure training value.
And S23, obtaining a pressure activation function according to the compressor outlet pressure training value and the compressor outlet pressure calculation value.
And S24, performing back propagation on the pressure analytic model to be trained through the pressure activation function to obtain the compressor outlet pressure analytic model.
Specifically, the training process of the compressor outlet pressure analytic model is similar to the training process of the turbine inlet temperature analytic model.
After the analysis value of the outlet pressure of the gas compressor is obtained by using the analysis model of the outlet pressure of the gas compressor, the analysis precision of the outlet pressure of the gas compressor can be calculated, namely:
acc can represent the analysis precision of the outlet pressure of the compressor; p may represent a measured compressor outlet pressure, PcMay represent an analytic value of compressor outlet pressure. Because the analysis precision of the outlet pressure of the compressor can reflect the quality of the input parameters of the analysis model of the outlet pressure of the compressor, when a fault occurs in the input parameters, the deviation between the analysis value of the outlet pressure of the compressor and the measured value is large, and the fault condition of the input parameters is reflected. The turbine inlet temperature analytic model and the compressor outlet pressure analytic model adopt the same input parameters, and the reliability of the turbine inlet temperature analytic model can be reflected by using Acc parameters, so that Acc can be used as the turbine inlet temperature confidence corresponding to the turbine inlet temperature analytic value.
And step 120, determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the combustion engine.
Specifically, the calculated turbine exhaust temperature may be calculated based on actual engine operating data. The fault values of the turbine exhaust temperatures measured by the plurality of turbine exhaust temperature thermocouples are removed, the highest values and the lowest values are removed, the average value of the residual turbine exhaust temperatures is calculated, and the calculated average value is used as the calculated value of the turbine exhaust temperatures participating in control and protection. The calculation method for calculating the confidence coefficient of the turbine exhaust temperature is as follows:
wherein Conf may represent turbine exhaust temperature confidence, k may represent the number of turbine exhaust temperature thermocouples, and k may representbThe number of turbine exhaust temperature thermocouple failures can be indicated.
And step 130, when the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is smaller than the threshold of the confidence coefficient of the exhaust temperature, taking the minimum value of the fuel output quantity corresponding to the analytic value of the turbine inlet temperature and the fuel output quantity corresponding to the calculated value of the turbine exhaust temperature as a target fuel output quantity, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
Fig. 2a is a first schematic diagram of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention, and as shown in fig. 2a, a fuel output amount corresponding to a calculated value of a turbine exhaust temperature may be calculated by using a PID algorithm. And (3) superposing the current fuel quantity after the deviation of the calculated value of the turbine exhaust temperature and the turbine exhaust temperature control reference passes through a PID (proportion integration differentiation) controller, and taking the superposed current fuel quantity as the fuel quantity output quantity of the turbine exhaust temperature control loop. The turbine exhaust temperature control references may include a turbine exhaust temperature control reference TTkn — 1 (isotherm reference), TTRXP (pressure ratio correction reference), TTRXS (fuel/power correction reference), and the like. Fig. 2b is a schematic diagram of a second principle in the heavy duty gas turbine control method according to an embodiment of the present invention, as shown in fig. 2b, using a relationship between a turbine inlet temperature and a turbine exhaust temperature, turbine inlet temperature control references T3_ TTKN _1, T3_ TTRXP, and T3_ TTRXS may be calculated, and then using a PID algorithm to calculate a fuel quantity corresponding to a turbine inlet temperature analytic value, that is, a deviation between the turbine inlet temperature analytic value and the turbine inlet temperature control reference, and after passing through a PID controller, superimposing a current fuel quantity as the fuel quantity output quantity of the turbine inlet temperature control loop.
FIG. 2C is a schematic diagram of a third principle of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention, as shown in FIG. 2C, when the turbine inlet temperature confidence is greater than or equal to the inlet temperature confidence threshold C1And the turbine exhaust temperature confidence is less than an exhaust temperature confidence threshold C2And then, a turbine inlet temperature control loop can be put into operation, the fuel output quantity corresponding to the turbine inlet temperature analytic value and the fuel output quantity corresponding to the turbine exhaust temperature calculated value are compared, and a smaller value is selected as the final target fuel output quantity to be added, so that the heavy-duty gas turbine can operate to the maximum power within the safe range.
Wherein, the confidence threshold C of the inlet temperature1Can represent the analytic precision threshold value of the turbine inlet temperature, and the analytic precision is generally required in practical application>99%, so the threshold C10.99 may be selected. Exhaust temperature confidence threshold C2The number of turbine exhaust temperature sensors that can tolerate faults may be measured, and when faults are not tolerated, the threshold may be set to 1; when tolerance of 1 is allowed, the constant value may be set to (n-3)/(n-2); when tolerance of 2 is allowed, the constant value may be set to (n-4)/(n-2), and so on.
The technical scheme of the embodiment obtains the actual operation data of the gas turbine, obtains the turbine inlet temperature analytic value and the corresponding turbine inlet temperature confidence coefficient through the pre-trained turbine inlet parameter analytic model, wherein the turbine inlet parameter analysis model comprises a turbine inlet temperature analysis model and a compressor outlet pressure analysis model, determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the combustion engine, when the turbine inlet temperature confidence is greater than or equal to the inlet temperature confidence threshold and the turbine exhaust temperature confidence is less than the exhaust temperature confidence threshold, the minimum value of the fuel output quantity corresponding to the turbine inlet temperature analytic value and the fuel output quantity corresponding to the turbine exhaust temperature calculation value is used as the target fuel output quantity, and the operation of the heavy gas turbine is controlled according to the target fuel output quantity, and the invention can realize the stable output of maximum power while avoiding the overtemperature damage of the gas turbine.
On the basis of the technical scheme, the heavy-duty gas turbine control method provided by the embodiment of the invention further comprises the following steps:
and step 140, when the confidence coefficient of the turbine inlet temperature is smaller than the threshold of the confidence coefficient of the inlet temperature or the confidence coefficient of the turbine exhaust temperature is larger than or equal to the threshold of the confidence coefficient of the exhaust temperature, taking the fuel output quantity corresponding to the calculated value of the turbine exhaust temperature as a target fuel output quantity, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
Specifically, as shown in FIG. 2C, when the turbine inlet temperature confidence is less than the inlet temperature confidence threshold C1Or the confidence coefficient of the turbine exhaust temperature is more than or equal to the threshold value C of the confidence coefficient of the exhaust temperature2And when the fuel output quantity is required to be added finally, the heavy-duty gas turbine is enabled to operate to the maximum power within a safe range.
It is understood that step 130 and step 140 have no sequential relationship between the execution of the preceding and the execution of the subsequent steps, and that step 130 and step 140 are two different engine temperature control conditions.
Step 150, if the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature, when the analytic value of the turbine inlet temperature is greater than or equal to the over-temperature threshold of the inlet temperature or the calculated value of the turbine exhaust temperature is greater than or equal to the over-temperature threshold of the exhaust temperature, performing over-temperature alarm operation on the gas turbine; and if the confidence coefficient of the turbine inlet temperature is smaller than the threshold value of the confidence coefficient of the inlet temperature, when the calculated value of the turbine exhaust temperature is larger than or equal to the over-temperature threshold value of the exhaust temperature, performing over-temperature alarm operation on the gas turbine.
Step 160, if the confidence coefficient of the turbine inlet temperature is smaller than the threshold of the confidence coefficient of the inlet temperature or the confidence coefficient of the turbine exhaust temperature is larger than or equal to the threshold of the confidence coefficient of the exhaust temperature, when the calculated value of the turbine exhaust temperature is larger than or equal to the threshold of the cutoff temperature of the exhaust temperature, the overtemperature cutoff operation of the gas turbine is carried out; and if the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is less than the threshold of the confidence coefficient of the exhaust temperature, performing the overtemperature interruption operation of the gas turbine when the analytic value of the turbine inlet temperature is greater than or equal to the threshold of the inlet temperature interruption and the calculated value of the turbine exhaust temperature is greater than or equal to the threshold of the exhaust temperature interruption.
FIG. 2d is a fourth schematic diagram of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention, as shown in FIG. 2d, when the resolved value of the turbine inlet temperature exceeds the inlet temperature over-temperature threshold, the turbine inlet temperature over-temperature alarm signal is output; and when the analytic value of the turbine inlet temperature value exceeds the inlet temperature interruption threshold value, outputting a turbine inlet temperature overtemperature interruption signal.
FIG. 2e is a schematic diagram illustrating a fifth principle of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention, as shown in FIG. 2e, when a calculated turbine exhaust temperature exceeds an exhaust temperature over-temperature threshold, a turbine exhaust temperature over-temperature alarm signal is output; and when the analytic value of the turbine exhaust temperature value exceeds the exhaust temperature cutoff threshold, outputting a turbine exhaust temperature overtemperature cutoff signal.
FIG. 2f is a schematic diagram illustrating a sixth principle of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention, when the turbine inlet temperature confidence is greater than or equal to the inlet temperature confidence threshold C, as shown in FIG. 2f1Any overtemperature between the turbine inlet temperature analytic value and the turbine exhaust temperature calculated value can generate overtemperature alarm; when the confidence coefficient of the turbine inlet temperature is smaller than the threshold value C of the confidence coefficient of the inlet temperature1And when the temperature analytical value of the turbine inlet is over-temperature, the turbine inlet does not participate in over-temperature alarm any more.
FIG. 2g is a schematic diagram illustrating a seventh principle of a method for controlling a heavy duty gas turbine according to an embodiment of the present invention, when the confidence of the turbine inlet temperature is less than the threshold C of the confidence of the inlet temperature, as shown in FIG. 2g1Or the confidence coefficient of the turbine exhaust temperature is more than or equal to the threshold value C of the confidence coefficient of the exhaust temperature2When the temperature of the turbine exhaust is over-temperature cutoff signals, the turbine exhaust temperature over-temperature cutoff signals can be directly output to the gas turbine over-temperature cutoff signals to carry out gas turbine over-temperature cutoff operation; when the confidence coefficient of the turbine inlet temperature is more than or equal to the threshold value C of the confidence coefficient of the inlet temperature1And confidence of turbine exhaust temperatureLess than exhaust temperature confidence threshold C2And outputting an overtemperature interruption signal of the gas turbine only when the turbine inlet temperature analytic value and the turbine exhaust temperature calculated value both reach an interruption threshold value, and performing overtemperature interruption operation on the gas turbine.
The overtemperature alarm and overtemperature interruption method provided by the embodiment can ensure that an overtemperature interruption signal is normally output when the turbine exhaust temperature sensor has no fault; and the method can also ensure that when the turbine exhaust temperature sensor fails, the unplanned shutdown of the combustion engine caused by the failure of the sensor of the unit is avoided.
Example two
The heavy-duty gas turbine control device provided by the embodiment of the invention can execute the heavy-duty gas turbine control method provided by any embodiment of the invention, and has corresponding functional modules and beneficial effects of the execution method. Fig. 3 is a block diagram of a heavy duty gas turbine control apparatus according to a second embodiment of the present invention, and as shown in fig. 3, the apparatus includes: a turbine inlet parameter resolution module 310, a turbine exhaust parameter resolution module 320, and a first fuel control module 330.
And the turbine inlet parameter analysis module 310 is configured to obtain actual operation data of the combustion engine, and obtain a turbine inlet temperature analysis value and a corresponding turbine inlet temperature confidence through a pre-trained turbine inlet parameter analysis model, where the turbine inlet parameter analysis model includes a turbine inlet temperature analysis model and a compressor outlet pressure analysis model.
And the turbine exhaust parameter calculation module 320 is configured to determine a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence according to the actual operation data of the combustion engine.
The first fuel control module 330 is configured to, when the turbine inlet temperature confidence is greater than or equal to an inlet temperature confidence threshold and the turbine exhaust temperature confidence is less than an exhaust temperature confidence threshold, take a fuel output amount corresponding to the turbine inlet temperature analytic value as a minimum target fuel output amount of the fuel output amounts corresponding to the turbine exhaust temperature calculated value, and control the operation of the heavy-duty gas turbine according to the target fuel output amount.
The technical scheme of the embodiment obtains the actual operation data of the gas turbine, obtains the turbine inlet temperature analytic value and the corresponding turbine inlet temperature confidence coefficient through the pre-trained turbine inlet parameter analytic model, wherein the turbine inlet parameter analysis model comprises a turbine inlet temperature analysis model and a compressor outlet pressure analysis model, determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the combustion engine, when the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is less than the threshold of the confidence coefficient of the exhaust temperature, taking the fuel output quantity corresponding to the analytic value of the turbine inlet temperature as the target fuel output quantity, and the operation of the heavy gas turbine is controlled according to the target fuel output quantity, and the invention can realize the stable output of maximum power while avoiding the overtemperature damage of the gas turbine.
Optionally, the turbine inlet parameter analyzing module 310 is specifically configured to:
acquiring actual operation data of the gas turbine, taking the actual operation data of the gas turbine as input data, and respectively inputting a pre-trained turbine inlet temperature analysis model and a pre-trained compressor outlet pressure analysis model to obtain a turbine inlet temperature analysis value and a compressor outlet pressure analysis value;
and obtaining the analysis precision of the pressure at the outlet of the gas compressor according to the analysis value of the pressure at the outlet of the gas compressor, and taking the analysis precision of the pressure at the outlet of the gas compressor as the confidence coefficient of the temperature at the inlet of the turbine.
Optionally, the training process of the turbine inlet temperature analytic model includes:
acquiring historical gas turbine operation data and a corresponding turbine inlet temperature calculation value in a historical time period;
inputting the historical gas turbine operation data into a temperature analysis model to be trained to obtain an output turbine inlet temperature training value;
obtaining a temperature activation function according to the turbine inlet temperature training value and the turbine inlet temperature calculation value;
carrying out back propagation on the temperature analytic model to be trained through the temperature activation function to obtain the turbine inlet temperature analytic model;
the training process of the gas compressor outlet pressure analytic model comprises the following steps:
acquiring historical gas turbine operation data in a historical time period and corresponding gas compressor outlet pressure calculated values;
inputting the historical gas turbine operation data into a pressure analysis model to be trained to obtain an output compressor outlet pressure training value;
obtaining a pressure activation function according to the compressor outlet pressure training value and the compressor outlet pressure calculation value;
and performing back propagation on the pressure analytic model to be trained through the pressure activation function to obtain the compressor outlet pressure analytic model.
Optionally, the apparatus further comprises a second fuel control module to:
and when the turbine inlet temperature confidence coefficient is smaller than the inlet temperature confidence coefficient threshold or the turbine exhaust temperature confidence coefficient is larger than or equal to the exhaust temperature confidence coefficient threshold, taking the fuel output quantity corresponding to the turbine exhaust temperature calculation value as a target fuel output quantity, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
Optionally, the apparatus further includes an over-temperature alarm module, configured to:
if the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature, when the analytic value of the turbine inlet temperature is greater than or equal to the threshold of the overtemperature of the inlet temperature or the calculated value of the turbine exhaust temperature is greater than or equal to the threshold of the overtemperature of the exhaust temperature, the overtemperature alarm operation of the gas turbine is carried out;
and if the confidence coefficient of the turbine inlet temperature is smaller than the threshold value of the confidence coefficient of the inlet temperature, when the calculated value of the turbine exhaust temperature is larger than or equal to the threshold value of the overtemperature of the exhaust temperature, performing overtemperature alarm operation on the gas turbine.
Optionally, the apparatus further comprises an over-temperature shutoff module, configured to:
if the confidence coefficient of the turbine inlet temperature is smaller than the threshold of the confidence coefficient of the inlet temperature or the confidence coefficient of the turbine exhaust temperature is larger than or equal to the threshold of the confidence coefficient of the exhaust temperature, when the calculated value of the turbine exhaust temperature is larger than or equal to the threshold of the cutoff temperature of the exhaust temperature, the overtemperature cutoff operation of the gas turbine is carried out;
and if the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is smaller than the threshold of the confidence coefficient of the exhaust temperature, when the analytic value of the turbine inlet temperature is greater than or equal to the threshold of the inlet temperature interruption and the calculated value of the turbine exhaust temperature is greater than or equal to the threshold of the exhaust temperature interruption, performing the overtemperature interruption operation of the gas turbine.
Optionally, the actual operation data of the combustion engine includes: ambient temperature, ambient pressure, compressor inlet guide vane angle, compressor outlet pressure, turbine outlet pressure, combustion engine speed, fuel quantity, and/or turbine exhaust temperature.
EXAMPLE III
Fig. 4 is a block diagram illustrating a heavy duty gas turbine control apparatus according to a third embodiment of the present invention, and as shown in fig. 4, the heavy duty gas turbine control apparatus includes a processor 410, a memory 420, and at least two signal collectors 430; the number of processors 410 in the heavy duty gas turbine control apparatus may be one or more, and one processor 410 is illustrated in fig. 4; the processor 410 and the memory 420 of the heavy duty gas turbine control device and the at least two signal collectors 430 may be connected by a bus or other means, and fig. 4 illustrates the bus connection as an example.
The memory 420 serves as a computer-readable storage medium that may be used to store software programs, computer-executable programs, and modules, such as program instructions/modules corresponding to the heavy duty gas turbine control method of embodiments of the present invention (e.g., the turbine inlet parameter analysis module 310, the turbine exhaust parameter calculation module 320, and the first fuel control module 330 in a heavy duty gas turbine control apparatus). The processor 410 executes various functional applications and data processing of the heavy duty gas turbine control apparatus by executing software programs, instructions and modules stored in the memory 420, i.e., implements the heavy duty gas turbine control method described above.
The memory 420 may mainly include a program storage area and a data storage area, wherein the program storage area may store an operating system, an application program required for at least one function; the storage data area may store data created according to the use of the terminal, and the like. Further, the memory 420 may include high speed random access memory, and may also include non-volatile memory, such as at least one magnetic disk storage device, flash memory device, or other non-volatile solid state storage device. In some examples, the memory 420 may further include memory remotely located from the processor 410, which may be connected to heavy duty gas turbine control equipment over a network. Examples of such networks include, but are not limited to, the internet, intranets, local area networks, mobile communication networks, and combinations thereof.
The signal collector 430 may be configured to collect actual operation data of the combustion engine, such as signal data of ambient temperature, ambient pressure, an inlet guide vane angle of the compressor, an outlet pressure of the turbine, a rotation speed of the combustion engine, a fuel amount, and a turbine exhaust temperature.
Example four
A fourth embodiment of the present invention also provides a storage medium containing computer executable instructions which, when executed by a computer processor, perform a method for heavy duty gas turbine control, the method comprising:
acquiring actual operation data of the gas turbine, and obtaining a turbine inlet temperature analytic value and a corresponding turbine inlet temperature confidence coefficient through a pre-trained turbine inlet parameter analytic model, wherein the turbine inlet parameter analytic model comprises a turbine inlet temperature analytic model and a compressor outlet pressure analytic model;
determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the gas turbine;
and when the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is smaller than the threshold of the confidence coefficient of the exhaust temperature, taking the fuel output quantity corresponding to the analytic value of the turbine inlet temperature as the minimum target fuel output quantity of the fuel output quantity corresponding to the calculated value of the turbine exhaust temperature, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
Of course, the embodiment of the present invention provides a storage medium containing computer-executable instructions, and the computer-executable instructions are not limited to the operations of the method described above, and can also perform related operations in the heavy-duty gas turbine control method provided by any embodiment of the present invention.
From the above description of the embodiments, it is obvious for those skilled in the art that the present invention can be implemented by software and necessary general hardware, and certainly, can also be implemented by hardware, but the former is a better embodiment in many cases. Based on such understanding, the technical solutions of the present invention may be embodied in the form of a software product, which can be stored in a computer-readable storage medium, such as a floppy disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a FLASH Memory (FLASH), a hard disk or an optical disk of a computer, and includes several instructions for enabling a computer device (which may be a personal computer, a server, or a network device) to execute the methods according to the embodiments of the present invention.
It should be noted that, in the embodiment of the heavy duty gas turbine control device, the included units and modules are only divided according to the functional logic, but are not limited to the above division as long as the corresponding functions can be realized; in addition, specific names of the functional units are only for convenience of distinguishing from each other, and are not used for limiting the protection scope of the present invention.
It is to be noted that the foregoing is only illustrative of the preferred embodiments of the present invention and the technical principles employed. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims (10)
1. A method of controlling a heavy duty gas turbine, comprising:
acquiring actual operation data of the gas turbine, and obtaining a turbine inlet temperature analytic value and a corresponding turbine inlet temperature confidence coefficient through a pre-trained turbine inlet parameter analytic model, wherein the turbine inlet parameter analytic model comprises a turbine inlet temperature analytic model and a compressor outlet pressure analytic model;
determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the gas turbine;
and when the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is smaller than the threshold of the confidence coefficient of the exhaust temperature, taking the minimum value of the fuel output quantity corresponding to the analytic value of the turbine inlet temperature and the fuel output quantity corresponding to the calculated value of the turbine exhaust temperature as a target fuel output quantity, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
2. The method of claim 1, wherein obtaining a turbine inlet temperature analytic value and a corresponding turbine inlet temperature confidence level via a pre-trained turbine inlet parameter analytic model comprises:
respectively inputting the actual operation data of the gas turbine as input data into a turbine inlet temperature analytical model and a compressor outlet pressure analytical model which are trained in advance to obtain a turbine inlet temperature analytical value and a compressor outlet pressure analytical value;
and obtaining the analysis precision of the pressure at the outlet of the gas compressor according to the analysis value of the pressure at the outlet of the gas compressor, and taking the analysis precision of the pressure at the outlet of the gas compressor as the confidence coefficient of the temperature at the inlet of the turbine.
3. The heavy duty gas turbine control method of claim 2,
the training process of the turbine inlet temperature analytic model comprises the following steps:
acquiring historical gas turbine operation data and a corresponding turbine inlet temperature calculation value in a historical time period;
inputting the historical gas turbine operation data into a temperature analysis model to be trained to obtain an output turbine inlet temperature training value;
obtaining a temperature activation function according to the turbine inlet temperature training value and the turbine inlet temperature calculation value;
carrying out back propagation on the temperature analytic model to be trained through the temperature activation function to obtain the turbine inlet temperature analytic model;
the training process of the gas compressor outlet pressure analytic model comprises the following steps:
acquiring historical gas turbine operation data in a historical time period and corresponding gas compressor outlet pressure calculated values;
inputting the historical gas turbine operation data into a pressure analysis model to be trained to obtain an output compressor outlet pressure training value;
obtaining a pressure activation function according to the compressor outlet pressure training value and the compressor outlet pressure calculation value;
and performing back propagation on the pressure analytic model to be trained through the pressure activation function to obtain the compressor outlet pressure analytic model.
4. The heavy duty gas turbine control method of claim 1, further comprising:
and when the turbine inlet temperature confidence coefficient is smaller than the inlet temperature confidence coefficient threshold or the turbine exhaust temperature confidence coefficient is larger than or equal to the exhaust temperature confidence coefficient threshold, taking the fuel output quantity corresponding to the turbine exhaust temperature calculation value as a target fuel output quantity, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
5. The heavy duty gas turbine control method of claim 1, further comprising:
if the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature, when the analytic value of the turbine inlet temperature is greater than or equal to the threshold of the overtemperature of the inlet temperature or the calculated value of the turbine exhaust temperature is greater than or equal to the threshold of the overtemperature of the exhaust temperature, the overtemperature alarm operation of the gas turbine is carried out;
and if the confidence coefficient of the turbine inlet temperature is smaller than the threshold value of the confidence coefficient of the inlet temperature, when the calculated value of the turbine exhaust temperature is larger than or equal to the threshold value of the overtemperature of the exhaust temperature, performing overtemperature alarm operation on the gas turbine.
6. The heavy duty gas turbine control method of claim 1, further comprising:
if the confidence coefficient of the turbine inlet temperature is smaller than the threshold of the confidence coefficient of the inlet temperature or the confidence coefficient of the turbine exhaust temperature is larger than or equal to the threshold of the confidence coefficient of the exhaust temperature, when the calculated value of the turbine exhaust temperature is larger than or equal to the threshold of the cutoff temperature of the exhaust temperature, the overtemperature cutoff operation of the gas turbine is carried out;
and if the confidence coefficient of the turbine inlet temperature is greater than or equal to the threshold of the confidence coefficient of the inlet temperature and the confidence coefficient of the turbine exhaust temperature is smaller than the threshold of the confidence coefficient of the exhaust temperature, when the analytic value of the turbine inlet temperature is greater than or equal to the threshold of the inlet temperature interruption and the calculated value of the turbine exhaust temperature is greater than or equal to the threshold of the exhaust temperature interruption, performing the overtemperature interruption operation of the gas turbine.
7. The heavy duty gas turbine control method of claim 1, wherein said actual engine operating data comprises: ambient temperature, ambient pressure, compressor inlet guide vane angle, compressor outlet pressure, turbine outlet pressure, combustion engine speed, fuel quantity, and/or turbine exhaust temperature.
8. A heavy duty gas turbine control apparatus, comprising:
the turbine inlet parameter analysis module is used for acquiring actual operation data of the gas turbine and obtaining a turbine inlet temperature analysis value and a corresponding turbine inlet temperature confidence coefficient through a pre-trained turbine inlet parameter analysis model, wherein the turbine inlet parameter analysis model comprises a turbine inlet temperature analysis model and a compressor outlet pressure analysis model;
the turbine exhaust parameter calculation module is used for determining a turbine exhaust temperature calculation value and a corresponding turbine exhaust temperature confidence coefficient according to the actual operation data of the gas turbine;
and the first fuel control module is used for taking the minimum value of the fuel output quantity corresponding to the turbine inlet temperature analytic value and the fuel output quantity corresponding to the turbine exhaust temperature calculated value as a target fuel output quantity when the turbine inlet temperature confidence coefficient is greater than or equal to an inlet temperature confidence coefficient threshold and the turbine exhaust temperature confidence coefficient is smaller than an exhaust temperature confidence coefficient threshold, and controlling the heavy-duty gas turbine to operate according to the target fuel output quantity.
9. A heavy duty gas turbine control apparatus, characterized in that the apparatus comprises:
one or more processors;
a memory for storing one or more programs;
the system comprises at least two signal collectors, a data acquisition unit and a data processing unit, wherein the signal collectors are used for collecting actual operation data of the combustion engine;
when executed by the one or more processors, cause the one or more processors to implement the heavy duty gas turbine control method of any of claims 1-7.
10. A storage medium containing computer executable instructions for performing the heavy duty gas turbine control method of any one of claims 1 to 7 when executed by a computer processor.
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